低速增升装置失速特性预测研究  

Prediction Research on Stall Characteristic for Low-speed High-lift System

作　　者：成水燕[1] 李中武[1] 聂智军[1] 梁益华[1] 

机构地区：[1]中航工业西安航空计算技术研究所,陕西西安710068

出　　处：《航空计算技术》2014年第3期27-32,共6页Aeronautical Computing Technique

基　　金：国家"863"计划项目资助(2012AA01A304)

摘　　要：民机低速增升装置失速特性是具有挑战性的空气动力学难题之一,决定着飞机起、降阶段机翼处于流动分离或尾迹干扰状态时的操纵稳定性,是气动设计必须关注的重要方面。利用基于N-S方程的自研多块结构网格计算软件和混合网格计算软件,对NASA高升力梯形机翼标准模型开展了失速特性计算研究,系统评估了计算软件、计算网格、湍流模型等主要因素对失速特性的影响,获得了有效预测高升力构型失速特性的计算方案,并将其成功应用于工程实际,为增升装置失速特性计算评估提供了有意义的参考。Stall characteristic of civil aircraft low-speed high-lift device is one of the challenging aerodynamics problems .It determines the control stability of wing in the flow separation or wake interference state when airplane is taking off and landing .It is an important aspect that aerodynamic design must be paying attention to .In this paper ,CFD computational study is performed on the standard model of NASA high-lift trapezoidal wing by using our in-house multi-block structured mesh solver and unstructured mesh solver based on RANS equation .Predictive capabilities for stall characteristic from solvers ,meshes and turbulence models are systematically evaluated .Calculation scheme which can effectively predict stall characteristic of high-lift configurations is obtained and it was applied in practical engineering successfully .The aim is to provide a meaningful guideline for stall characteristic prediction of civil aircraft high-lift system .

关 键 词：民机 增升装置 失速特性 数值模拟 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]